Patents Examined by Kayla McCaffrey
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Patent number: 10954885Abstract: A flow guiding appliance of a turbomachine, in particular of an aircraft engine, for a partial exit flow of an outlet guide vane of a compressor, wherein, a flow guiding element delimits an annular channel about a shaft of the turbomachine. A frictional engagement connecting surface at the circumference of the flow guiding element connects the flow guiding element to another structural component of the turbomachine. The frictional engagement connecting surface with a closed enveloping surface can be inserted in a deformed state into the structural component with a circular cylindrical sealing surface with at least two opposite points. The at least two points of the closed enveloping surface are arranged in at least two opposite frictionally engaged contact areas of the circular cylindrical sealing surface following deformation. The invention also relates to a method for creating a flow guiding element.Type: GrantFiled: May 3, 2018Date of Patent: March 23, 2021Assignee: Rolls-Royce Deutschland Ltd & Co KGInventors: Igor Sikorski, Jason Phillips
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Patent number: 10946955Abstract: A propulsion assembly for a rotorcraft includes a mast and a proprotor hub assembly coupled to the mast and having a gimballing degree of freedom relative to the mast. The proprotor hub assembly includes a hook receiver. The propulsion assembly includes a gimbal lock positioned about the mast. The gimbal lock includes a locking ring and a gimbal lock hook. The gimbal lock is movable between a disengaged position and an engaged position relative to the proprotor hub assembly. The gimbal lock enables the gimballing degree of freedom in the disengaged position and disables the gimballing degree of freedom in the engaged position. The gimbal lock hook is hooked to the hook receiver in the engaged position to secure the locking ring to the proprotor hub assembly.Type: GrantFiled: July 31, 2018Date of Patent: March 16, 2021Assignee: Textron Innovations Inc.Inventors: Troy Cyril Schank, Andrew Ryan Maresh, Chyau-Song Tzeng
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Patent number: 10933985Abstract: A propulsion assembly for a rotorcraft includes a mast and a proprotor hub assembly coupled to the mast and having a gimballing degree of freedom relative to the mast. The propulsion assembly includes a gimbal lock assembly positioned about the mast and including a plurality of radially outwardly extending and circumferentially distributed rollers. The gimbal lock assembly is movable between a disengaged position and an engaged position relative to the proprotor hub assembly. In the disengaged position, the gimbal lock assembly enables the gimballing degree of freedom. In the engaged position, the rollers of the gimbal lock assembly contact the proprotor hub assembly to disable the gimballing degree.Type: GrantFiled: July 31, 2018Date of Patent: March 2, 2021Assignee: Textron Innovations Inc.Inventors: Troy Cyril Schank, Andrew Ryan Maresh, Chyau-Song Tzeng
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Patent number: 10935046Abstract: A gas turbine engine fan case may comprise a plurality of wound layers that form a laminate and have a nominal radial fan case thickness, where the laminate includes a plurality of discrete fan case radial locations comprising a plurality of radially stacked composite plies that form a radial integral build up in comparison to the nominal radial fan case thickness.Type: GrantFiled: April 19, 2018Date of Patent: March 2, 2021Assignee: Raytheon Technologies CorporationInventors: David R. Lyders, Colin J. Kling
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Patent number: 10927837Abstract: A centrifugal pump includes a selectable regenerative style pumping element, including a regenerative pump rotor and at least one side wall flow channel formed by a rotating disc. The regenerative pumping element is selectable between a first state in which the disc does not rotate with the impeller and a second state in which the disc rotates with the impeller.Type: GrantFiled: November 2, 2016Date of Patent: February 23, 2021Assignee: EATON INTELLIGENT POWER LIMITEDInventor: Martin A. Clements
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Patent number: 10890073Abstract: A turbine blade (43a) is provided with a blade main body (51) and a tip shroud (52). The blade main body (51) is provided with a leading edge-side cooling passage (64), a trailing edge-side cooling passage (67), and a middle cooling passage (65). The tip shroud (52) is provided with a first discharge passage (72), a second discharge passage (73), and a third discharge passage (74). The first discharge passage (72) discharges a cooling medium flowing through the leading edge-side cooling passage (64). The second discharge passage (73) discharges a cooling medium flowing through the trailing edge-side cooling passage (67). The third discharge passage (74) discharges a cooling medium flowing through the middle cooling passage (65).Type: GrantFiled: August 23, 2016Date of Patent: January 12, 2021Assignee: MITSUBISHI POWER, LTD.Inventors: Keita Takamura, Satoshi Hada, Hidekatsu Atsumi
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Patent number: 10871076Abstract: A rotating unit of a steam turbine includes a rotor; a bucket coupled to the rotor to convert fluid energy into mechanical work, the coupled bucket being pre-twisted at a predetermined angle, the bucket having a base surface facing a point of coupling between the rotor and the bucket; and bucket support means, provided at the point of coupling between the rotor and the bucket, for supporting a twisted state of the bucket based on the coupling between the rotor and the bucket, thereby enabling the twisting of the bucket to be maintained during operation. In a steam turbine including the rotating unit, it is possible to reduce vibration occurring during operation and to increase the contact force between a cover formed at the blade tip of the bucket and a cover of another bucket to prevent a leakage of steam between adjacent covers.Type: GrantFiled: March 22, 2018Date of Patent: December 22, 2020Assignee: Doosan Heavy Industries Construction Co., LtdInventor: Seok Jin Jang
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Patent number: 10830092Abstract: Rotor thrust balancing systems for turbomachines and methods of using the same are generally disclosed. For example, a rotor thrust balancing system for a turbomachine, wherein the turbomachine defines a centerline extending the length of the turbomachine. The system includes a rotating drive shaft, a thrust bearing, and a first waveguide sensor. The rotating drive shaft couples a turbine section and a compressor section of the turbomachine. The thrust bearing supports the rotating drive shaft of the turbomachine. The thrust bearing includes a plurality of ball bearings, an inner race coupled to the rotating drive shaft, and an outer race coupled to a fixed structure. The first waveguide sensor is coupled to the outer race at a first end of the waveguide sensor. The waveguide sensor communicates a vibrational frequency from the thrust bearing to a second end of the waveguide sensor.Type: GrantFiled: March 7, 2018Date of Patent: November 10, 2020Assignee: General Electric CompanyInventors: Kyle Robert Snow, Andrew Michael Tompkins, Andrew Michael Watson, Philip Joseph Ogston, Christopher Michael Thompson
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Patent number: 10823191Abstract: The present disclosure is directed to a gas turbine engine including a first frame comprising a first bearing assembly, a second frame comprising a second bearing assembly, and a compressor rotor. A first stage compressor airfoil is defined at an upstream-most stage of the compressor rotor. The compressor rotor is rotatable via the first bearing assembly and the second bearing assembly. The first stage compressor airfoil is disposed between the first bearing assembly and the second bearing assembly.Type: GrantFiled: March 15, 2018Date of Patent: November 3, 2020Assignee: General Electric CompanyInventors: Veeraraju Vanapalli, Bhaskar Nanda Mondal, Rajendra Mahadeorao Wankhade, Ramana Reddy Kollam
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Patent number: 10801352Abstract: The invention concerns a turbine for a gas turbine comprising a blade, a vane and an abradable lip attached to the blade or to the vane, wherein the blade and the vane are separated by a gap and the abradable lip extends part of the distance across the gap. Embodiments include the addition of an abrasive layer attached on the other side of the gap from the abradable lip. A method of manufacturing is also described.Type: GrantFiled: April 21, 2016Date of Patent: October 13, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Guillaume Wagner, Herbert Brandl, Emanuele Facchinetti, Matthias Hoebel, Carlos Simon-Delgado
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Patent number: 10801506Abstract: A fixing bolt for a stationary member, the bolt extending through and fixing a plurality of stationary members in a multistage centrifugal compressor, includes a head portion, a columnar portion connected to the head portion, and a threaded portion connected to the columnar portion. The columnar portion includes one or more large diameter parts and a plurality of small diameter parts, the one or more large diameter parts each corresponding to a position of an antinode of a primary vibration mode of the fixing bolt for the stationary member, or to the position of the antinode of the primary vibration mode and positions of antinodes of a secondary vibration mode of the fixing bolt for the stationary member, and each of the plurality of small diameter parts having a diameter smaller than each of the large diameter parts.Type: GrantFiled: November 27, 2015Date of Patent: October 13, 2020Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATIONInventor: Yoshiaki Shoji
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Patent number: 10801339Abstract: A variable pitch fan assembly includes variable pitch fan blades circumscribed about engine centerline axis coupled to a drive shaft centered about the engine centerline axis. Each blade pivotable about pitch axis perpendicular to centerline axis and having blade turning lever connected thereto. One or more linear actuators non-rotatably mounted parallel to engine centerline axis and operably linked to fan blades for pivoting fan blades and connected to spider ring through thrust bearings for transmission of axial displacement of non-rotatable actuator rods of actuators while the fan blades are rotating. Spider arms extending away from spider ring towards blade roots and each spider arm connected to one of the turning levers. Turning levers may be connected and caromed to spider arms by pin and slot joint. Each spider arm may include joint pin disposed through joint slot of turning lever. Joint slot may be angled or curved.Type: GrantFiled: July 11, 2017Date of Patent: October 13, 2020Assignee: General Electric CompanyInventors: Aldo Daniel Lopez Guzman, Alberto del Angel Duran, Daniela Martinez Arteaga, Carla Garcia Lopez de Llergo, Ileana Prisabel Corona Acosta
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Patent number: 10794213Abstract: A compressor shroud assembly in a turbine engine having a dynamically moveable shroud for encasing a rotor segment. The rotor segment comprises a bladed disc. The compressor shroud assembly maintains a clearance gap between the shroud and the blade tips of the bladed disc. The assembly comprises a static compressor casing, a shroud mounted to the casing, and an actuator mounted to the casing. The shroud comprises a flowpath boundary member spaced radially inward from the casing, the flowpath boundary member being moveable relative to the casing in a radial direction. The actuator is coupled to the shroud for effecting the movement of the flowpath boundary member.Type: GrantFiled: January 4, 2017Date of Patent: October 6, 2020Assignee: Rolls-Royce North American Technologies Inc.Inventors: Douglas D. Dierksmeier, Edward C. Rice, Ryan C. Humes
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Patent number: 10794193Abstract: An air foil includes a body and a filler. The body may include a chamber formed therein and includes a first metallic material. The filler may at least partially occupy the chamber of the body and may include a second metallic material. The second metallic material may have a comparatively more negative electrode potential than the first metallic material.Type: GrantFiled: August 23, 2016Date of Patent: October 6, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Daniel Bernard Kupratis, Mary Colby, Paul R Hanrahan, Frederick M Schwarz
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Patent number: 10794358Abstract: A blade for a wind turbine can include an elongated and curved sheet having a root, a tip positioned opposite the root, a leading edge spanning between the root and the tip along a length of the blade, and a trailing edge spanning between the root and the tip opposite the leading edge. The blade can include a generally concave surface formed by curvature of the blade about a longitudinal axis. The blade can further include one or more air dams, which can be in the form of strip elements oriented transverse to the longitudinal axis and extending away from the concave surface. The air dams improve torque and efficiency of the blade. In some embodiments, an edge of the root can include a plurality of curved projections distributed thereon. A wind turbine system can include a generator and a wind turbine having a mounting element to support turbine blades.Type: GrantFiled: February 9, 2018Date of Patent: October 6, 2020Assignee: Primo Energy, Inc.Inventors: Edward McMahon, Lauren Hoffman
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Patent number: 10787928Abstract: A casing for use in a turbofan engine is provided. The casing includes an inner hub, an intermediate casing positioned radially outward from the inner hub, an outer casing positioned radially outward from the intermediate casing, and a plurality of struts spaced circumferentially about the inner hub and extending between the inner hub and the outer casing. At least one strut of the plurality of struts includes a flow channel extending therethrough. The casing also includes a fluid scoop defined within the inner hub, and a collector that couples the fluid scoop in flow communication with the flow channel.Type: GrantFiled: November 30, 2016Date of Patent: September 29, 2020Assignees: General Electric Company, GE Avio, S.r.l.Inventors: Andrew Michael Tompkins, Brandon Wayne Miller, Donald Albert Bradley, Michele Gravina, Daniel Alan Niergarth, Lorenzo Cipolla
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Patent number: 10774840Abstract: A fan blade capable of cooling an enclosed space is disclosed, comprising: a leading edge; a trailing edge; a top side; a bottom side; and a plurality of passageways wherein each of the passageways narrows within the fan blade. The plurality of passageways may narrow at any point within the interior of the fan blade and may be shaped in any way to ensure that a narrowing occurs. The plurality of passageways may also be in thermal communication with the rest of the fan blade. The fan blades may be used as part of a fan having a hub and a plurality of fan blades. Also disclosed, is a method of cooling a room comprising rotating a fan, the fan comprising: a plurality of fan blades, each fan blade having a plurality of passageways, wherein each of the passageways narrows within the fan blade.Type: GrantFiled: May 10, 2018Date of Patent: September 15, 2020Assignee: COOL-AIR LLC.Inventor: Lance B. Young
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Patent number: 10753209Abstract: A turbine disc assembly is provided. The turbine disc assembly includes a first rotor disc, a second rotor disc, and a spacer disc coupled between the first and second rotor discs along an axis to define a plenum. The spacer disc has an inner surface with a radius from the axis. A first cooling channel defined between the first rotor disc and the spacer disc is in flow communication with the plenum. The second rotor disc includes a deflector having a deflection surface positioned within the plenum such that the deflection surface is oriented towards the first cooling channel at an acute angle relative to the radius of the inner surface of the spacer disc.Type: GrantFiled: June 22, 2016Date of Patent: August 25, 2020Assignee: General Electric CompanyInventors: Sudhakar Neeli, Sanjeev Kumar Jain
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Patent number: 10745117Abstract: A quill shaft which translates rotational energy between a gear and a drive shaft having a drive shaft spline includes a first leg having an inner spline which meshes with the drive shaft spline and a second leg concentric with the first leg and radially offset and separated from the first leg by a gap. The second leg includes an outer spline which meshes with the gear. The first leg is connected to the second leg at one end to allow for change to a gap size during while translating the rotational energy between the gear and a drive shaft.Type: GrantFiled: April 22, 2015Date of Patent: August 18, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Todd A. Garcia, Bryan Kenneth Baskin, Huali Ding, Biqiang Xu
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Patent number: 10746047Abstract: A gas turbine engine including a first rotor assembly is generally provided. The first rotor assembly includes outer drum and an outer drum airfoil. The outer drum airfoil is coupled to the outer drum and extended inward along a radial direction. A damper structure is coupled to one or more of the outer drum or the outer drum airfoil.Type: GrantFiled: October 27, 2017Date of Patent: August 18, 2020Assignee: General Electric CompanyInventors: Richard Alan Wesling, Darek Tomasz Zatorski, Gert Johannes van der Merwe